Armstrong Whitworth Atlas Aircraft

Production Details

Design Company:

Sir W.G. Armstrong Whitworth Aircraft Ltd

First Flight:

10 May 1925

Atlas Prototype:

1 - Sir W.G. Armstrong Whitworth Aircraft Ltd

Atlas I:

460 - Sir W.G. Armstrong Whitworth Aircraft Ltd

Atlas II:

17 - Sir W.G. Armstrong Whitworth Aircraft Ltd

Type Specification

Applies to:

Armstrong Whitworth Atlas I

Type:

Two seat Army co-operation biplane

Wing:

Single bay biplane. Wings are swept at 6 degrees. Lower wing is shorter than upper and is attached at the base of the fuselage. Upper wing is supported on a cabane of steel tubes in the form of a W. Wing structure is of corrugated steel strip covered in fabric. Balanced ailerons on upper wings only

Fuselage:

Fuselage structure on steel tube. Sides and bottom of fuselage are faired by formers and stringers, while the top decking consists of a wooden fairing around the cockpits

Tail Unit:

Tailplane mounted at top of fuselage of cantilever design. Balanced elevator and balanced rudder

Landing Gear:

Cross axle type. Axle carried on Vees. Tail skid

Power Plant:

One 400 hp Jaguar IVC

Accommodation:

Pilot seated in forward cockpit, observer behind

Span:

39 ft 7 in

Length:

28 ft 7 in

Height:

10 ft 6 in

Wing Area:

391 sq ft

Empty:

2,550 lb

Max:

4,020 lb

Max Speed:

142 mph at sea level

Climb:

28 min to 15,000 ft

Service Ceiling:

16,800 ft

Endurance:

3.25 hr

Preserved in British Museums

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